An aerodynamic arm for an aircraft turbine engine casing includes a tubular outer shell having a generally elongate shape extending substantially along an axis. The shell has axial ends configured to be connected to a turbine engine casing. An electrically conductive core extends inside the shell and has ends configured to electrically connect to the ends of the shell. An insulating material occupies a space between the core and the shell.

A fan of the present disclosure includes a housing, an air guiding device, and a fan blade, where the an guiding device and the fan blade are arranged in the housing, and the an guiding device is used to guide air. The air guiding device includes a fixed ring. A limiting-position device is arranged in the fan, and is structured and arranged to limit and fix the air guiding device, which makes the air guiding device not shake and firmly fixes the air guiding device in the housing of the fan, further makes the air guiding device maintain a normal working state.

Apparatus and methods are described including coupling a rigid tube to a drive cable that comprises a plurality of coiled wires, by placing ends of the drive cable and the rigid tube at a given location within a butt-welding overtube. The ends of the drive cable and the rigid tube are visible when they are disposed at the given location within the butt-welding overtube, via a window defined by the butt-welding overtube. The placement of the drive cable within the butt-welding overtube is such that a helical groove within a portion of the butt-welding overtube is disposed over the drive cable. Welding rings are formed around the butt-welding overtube. Other applications are also described.

A counter rotating axial air moving device structure is disclosed. The rear rotor includes a rear hub and rear blades, and a pitch angle of each of the rear blades increases gradually in a direction away from the rear hub. The front rotor, the rear rotor and the stator component are stacked with each other. The ratio of the thickness to the diameter is equal to or greater than about 0.25 and equal to or less than about 0.8. Therefore, a better performance curve is obtained, and the vibration and noise are avoided.

A tubeaxial fan housing has a planar support vane that is fixed at sides thereof to opposing interior sides of the tubular housing, toward an inlet of the housing. The support vane receives a shaft on an underside thereof, upon which a propeller is mounted near an outlet end of the housing. The support vane has a curved edge facing the propeller to change a pattern of eddies generated downstream of the support plate and thereby reduce the noise generated by the fan. The curve is an S-shape and may be a sine wave whose period is ⅕ the propeller diameter. The propeller is positioned a relatively large distance from the curved edge of the support vane to reduce further the generation of eddies. That is, the closest point of the curved edge to the propeller is one chord length, which chord is at a tip of a propeller blade. A rounded inlet bell on the housing includes a rounded surface to reduce further turbulence across the propeller and support vane to further reduce sound. The propeller has only five blades to further reduce the generation of eddies.

An integral fan and airflow guide including a hub having a frusto-conical outer surface, and a plurality of fan blades circumferentially spaced apart about the hub and radiating outwardly from the hub. The frusto-conical outer surface having a plurality of circumferentially spaced apart slots that separate inclined segments of the outer surface to define respective airflow guide surfaces. The plurality of fan blades are integral with the respective airflow guide surfaces. The inclined airflow guide surfaces cooperate with the fan blades to direct impelled air axially and radially outwardly for improving the cooling of a machine component, such as a hydrostatic transmission, that is obstructed from airflow by a pulley or other obstacle.

A split casing fluid device includes a reaction chamber including a first and second casings having a portions of a stator, a rotor rotatably mounted inside the stator and having a plurality of fluid-interacting features, the rotor exterior surface and the stator define a fluid passageway therebetween, an inlet into the reaction chamber in fluid communication with the fluid passageway, and an outlet from the reaction chamber in fluid communication with the fluid passageway. Removal of a casing creates an opening in the reaction chamber sized to allow passing the rotor through the opening. In some embodiments, the casings span the entire length of the rotor and removal of at least one casing creates an opening in the reaction chamber sized to allow removal of the rotor in a perpendicular direction to the longitudinal axis. The fluid device may be a cavitation generator with a rotor having cavitation-inducing features.

A supporting structure for a gas turbine engine includes an inner ring, an outer ring, and a plurality of circumferentially spaced, load carrying radial elements connecting the inner and outer rings. The radial elements have an airfoil shape with a leading edge directed towards the inlet side of the supporting structure, a trailing edge directed towards the outlet side of the supporting structure, and two opposite sides connecting the leading edge and the trailing edge. At least one of the radial elements includes a gas passage arrangement configured to lead a separate bleeding gas flow from the supporting structure. The gas passage arrangement includes a radially extending gas channel arranged inside the radial element and at least one opening in communication with the gas channel. The at least one opening is arranged at one of the two opposite sides of the radial element.

A closer for an attachment orifice of an OGV in a turbine engine, the vane having a blade fixed to a root provided with attachment orifices, the closer including a cup adapted to be fixed in the attachment orifice of an OGV; a cylindrical shaped plug engaging in the cup, the plug including an upper face inclined relative to the ground plane of the plug; a guide adapted to position the plug on the cup by rotation into a working position, in which the upper face of the plug coincides with the surface level of the vane root; a blocking system to block the plug in the working position.

A blade row group arrangeable in a main flow path of a fluid-flow machine includes N adjacent member blade rows firmly arranged relative to each other in both a meridional direction (m) and a circumferential direction (u). A relative secondary passage length (v′) and a relative secondary passage width (w′) each increase at least in one part of the area between the mean meridional flow line (SLM) and at least one of the main flow path boundaries (HB) towards the main flow path boundary (HB).